EP3217016B1 - Turbomachine - Google Patents
Turbomachine Download PDFInfo
- Publication number
- EP3217016B1 EP3217016B1 EP17000320.6A EP17000320A EP3217016B1 EP 3217016 B1 EP3217016 B1 EP 3217016B1 EP 17000320 A EP17000320 A EP 17000320A EP 3217016 B1 EP3217016 B1 EP 3217016B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- axial
- grooves
- turbomachine
- rotor
- shaft sealing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000007789 sealing Methods 0.000 claims description 93
- 239000012530 fluid Substances 0.000 claims description 46
- 239000007788 liquid Substances 0.000 claims description 11
- 238000010586 diagram Methods 0.000 description 43
- 230000000694 effects Effects 0.000 description 10
- 238000013016 damping Methods 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/106—Shaft sealings especially adapted for liquid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D1/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D1/06—Multi-stage pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/04—Shafts or bearings, or assemblies thereof
- F04D29/046—Bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/12—Shaft sealings using sealing-rings
- F04D29/126—Shaft sealings using sealing-rings especially adapted for liquid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/165—Sealings between pressure and suction sides especially adapted for liquid pumps
- F04D29/167—Sealings between pressure and suction sides especially adapted for liquid pumps of a centrifugal flow wheel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/426—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for liquid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/669—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for liquid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
Description
- This application claims priority to Japanese Patent Application No.
JP2016-046891, filed on March 10, 2016 - The present invention concerns a turbomachine and, in particular, relates to a structure of a shaft sealing device which handles a liquid as a working fluid such as a centrifugal pump, a pump turbine and so forth.
- The turbomachine such as the centrifugal pump and so forth is mainly provided with a rotor having an impeller, a bearing which rotatably supports the rotor, a casing which contains therein the rotor and forms a stationary flow passage and so forth. In addition, the impeller imparts a dynamic pressure to the working fluid by rotating the rotor, converts the dynamic pressure into a static pressure at a part on the stationary flow passage which is formed in the-casing, and thereby feeds the high-pressure working fluid under pressure to a demander and so forth.
- Part of the working fluid which has been sucked into the turbomachine leaks through a gap part between the casing and the rotor. In order to reduce this leakage flow, the shaft sealing device is installed in the gap part between the casing and the rotor.
- In a case of the centrifugal pump acting as the turbomachine which handles the liquid as the working fluid, in the centrifugal pump which is described, for example, in Japanese Unexamined Patent Application Publication No.
Hei 10-259799 - In the labyrinth shaft sealing device which is described in this Japanese Unexamined Patent Application Publication No.
Hei 10-259799 FIG. 9 thereof. In addition, a width (a length in the axial direction) of the land part and a width (a length in the axial direction) of the groove part are configured to be almost the same as each other. - Incidentally, in a centrifugal compressor which handles a gas as the working fluid, for example, as indicated in Japanese Unexamined Patent Application Publication No.
2014-74360 FIG. 2 and FIG. 3 in Japanese Unexamined Patent Application Publication No.2014-74360 2014-74360 -
- [Patent Literature 1] Japanese Unexamined Patent Application Publication No.
Hei 10-259799 - [Patent Literature 2] Japanese Unexamined Patent Application Publication No.
2014-74360 - Furtermore,
US 4 545 586 A discloses a turbomachine with the features in the preamble ofpresent claim 1. Another conventional turbomachine is described inEP 2 899 405 A1 - Since the leakage flow which flows into the labyrinth shaft sealing device turns into a swirling flow which swirls along a rotation direction of the rotor and flows in the axial direction, the unstable fluid force which would further encourage swirling movement in the circumferential direction caused by vibration is generated on a part of the labyrinth shaft sealing device relative to the rotor due to an interaction between this flow and the vibration of the rotor. Therefore, it has been found that the possibility that an unstable vibration may be generated in the rotor becomes large.
- Accordingly, in order to prevent this unstable vibration of the rotor, it is effective to promote a reduction in swirling flow in the shaft sealing device and to improve vibration damping property of the shaft sealing device. However, in the labyrinth shaft sealing device described in Japanese Unexamined Patent Application Publication No.
Hei 10-259799 - The pocket damper shaft sealing device described in the above-mentioned
Patent Literature 2 is provided with a plurality of grooves which are arranged in parallel with one another and intermittently in the circumferential direction of the rotor and each of the grooves has a pocket structure owing to which the groove does not communicate with other grooves in the circumferential direction. Therefore, in the working fluid which has flown into the pockets, an amount of the working fluid which escapes in the circumferential direction when displacing the rotor is reduced and therefore the vibration damping property of the shaft sealing device is improved. In addition, since the grooves which are formed in the circumferential direction do not communicate with one another, the swirling flow which would cause generation of the unstable fluid force is suppressed and also the unstable fluid force is reduced. - However, the pocket damper shaft sealing device described in this
Patent Literature 2 is the shaft sealing device for the gas as illustrated inFIG. 2 thereof and a part corresponding to the land part described in Japanese Unexamined Patent Application Publication No.Hei 10-259799 - When adopting such a shaft sealing device for the gas as mentioned above as the shaft sealing device for a turbomachine which handles a liquid which is higher in viscosity than the gas, since the width of the part corresponding to the land part is thin, it becomes difficult to sufficiently utilize an energy loss effect which is brought about by the viscous friction of the working fluid and therefore there is the possibility that the leakage flow may not be sufficiently reduced.
- An object of the present invention is to obtain a turbomachine which is capable of reducing leakage of the working fluid and capable of also reducing the unstable fluid force which acts on a rotor in a shaft sealing device for the turbomachine which handles a liquid as the working fluid.
- In order to attain the above-mentioned object, the present invention provides a turbomachine as defined in
claim 1. The subclaims relate to preferred embodiments. The turbomachine includes a rotor having an impeller, a bearing which rotatably supports the rotor, a casing which contains the rotor therein and forms a stationary flow passage, and a shaft sealing device which reduces leakage of a working fluid through a gap part between the casing and the rotor, in which the working fluid is a liquid and a plurality of axial grooves which are long in an axial direction and short in a circumferential direction of the rotor, which have been intermittently arranged in an axial direction and a circumferential direction of the rotor with a land part being interposed between the adjacent axial grooves, and which are provided in an inner circumferential surface of the shaft sealing device. - Also diclosed is a turbomachine that includes a rotor having an impeller, a bearing which rotatably supports the rotor, a casing which contains the rotor therein and forms a stationary flow passage and a shaft sealing device which reduces leakage of a working fluid through a gap part between the casing and the rotor, in which the working fluid is a liquid, an axial groove group which includes axial grooves which have been intermittently arranged on the same straight line directed in an axial direction with a land part being interposed between the adjacent axial grooves, is provided in an inner circumferential surface of the shaft sealing device, and a plurality of the axial groove groups are adjacently arranged in the circumferential direction, and the plurality of axial groove groups which have been adjacently arranged in the circumferential direction are arranged so as to be parallel with one another with the land part being interposed between the adjacent axial groove groups.
- According to the present invention, there is an advantageous effect that it is possible to obtain the turbomachine which is capable of reducing the leakage of the working fluid in the shaft sealing device for the turbomachine which handles the liquid as the working fluid and is also capable of reducing the unstable fluid force which acts on the rotor. Brief Description of Drawings
-
FIG. 1 is a partial longitudinal sectional diagram illustrating anembodiment 1 of a turbomachine of the present invention. -
FIG. 2 is a diagram illustrating an inner surface shape of a shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the main part development diagram illustrating the shaft sealing device by developing the device in a circumferential direction. -
FIG. 3 is a sectional diagram on arrow along the III-III line in FIG. -
FIG. 4 is a diagram illustrating a first modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram corresponding to the diagram inFIG. 2 . -
FIG. 5 is a sectional diagram on arrow along the V-V line inFIG. 4 . -
FIG. 6 is a diagram illustrating a second modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram corresponding to the diagram inFIG. 2 . -
FIG.7 is a sectional diagram on arrow along the VII-VII line in FIG. -
FIG. 8 is a diagram illustrating a third modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram corresponding to the diagram inFIG. 2 . -
FIG. 9 is a sectional diagram on arrow along the IX-IX line in FIG. -
FIG. 10 is a diagram illustrating a fourth modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram corresponding to the diagram inFIG. 2 . -
FIG. 11 is a sectional diagram on arrow along the XI-XI line in FIG. -
FIG. 12 is a diagram illustrating a fifth modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram corresponding to the diagram inFIG. 2 . -
FIG. 13 is a sectional diagram on arrow along the XIII-XIII line inFIG. 12 . - In the following, specific embodiments of the turbomachine of the present invention will be described on the basis of the appended drawings. In the respective drawings, parts designated by the same numerals indicate the same or corresponding parts.
- The
embodiment 1 of a turbomachine of the present invention will be described usingFIG. 1 to FIG. 3 . -
FIG. 1 is a partial longitudinal sectional diagram illustrating a uniaxial multistage centrifugal pump as aturbomachine 1 of the present invention. First, an overall configuration of theturbomachine 1 of thepresent embodiment 1 will be described with reference toFIG. 1 . Incidentally, as the uniaxial multistage centrifugal pump, for example, a boiler feed pump and so forth are available. - In
FIG. 1 , theturbomachine 1 of the present embodiment is configured by arotor 3 having animpeller 2, a bearing (not illustrated) which rotatably supports thisrotor 3, an inner-side casing (an inner casing) 5 which contains therotor 3 therein and forms astationary flow passage 4, an outer-side casing (an outer casing) 6 which contains the inner-side casing 5 therein and so forth. Thestationary flow passage 4 is provided with adiffuser vane 7 which has been provided on the discharge side of theimpeller 2 and areturn vane 8 which has been provided on the next-stage impeller 2 side. - In addition, a wearing
ring 9a is provided on an inner surface of a stationary part (an inner surface of thecasing 5 in this embodiment) which faces an outer circumferential surface of amouth ring part 2a of theimpeller 2 and this wearingring 9a configures one labyrinthshaft sealing device 9 which seals a gap between themouth ring part 2a of theimpeller 2 and the stationary part. - A
cylindrical part 2b is provided on the rear face side of theimpeller 2, astage bush 9b is provided on the inner surface of the stationary part (the inner surface of the casing 5) which faces an outer circumferential surface of thiscylindrical part 2b, and thisstage bush 9b configures another labyrinthshaft sealing device 9 which seals a gap between thecylindrical part 2b of theimpeller 2 and the stationary part. - 10 denotes a balance drum adapted to achieve a balance of thrust force which acts on the
rotor 3, a balance drumshaft sealing device 9c is provided on the inner surface of the stationary part (the inner surface of thecasing 5 or 6) which faces an outer circumferential surface of thisbalance drum 10, and this balance drumshaft sealing device 9c configures a further labyrinthshaft sealing device 9 which seals a gap between thebalance drum 10 and the stationary part. - Next, an operation of the
turbomachine 1 which is configured as mentioned above will be described. The working fluid (a liquid such as water and so forth in this embodiment) is sucked into theimpeller 2 by rotating therotor 3, is discharged onto thestationary flow passage 4 by being applied with a dynamic pressure by thisimpeller 2 and the dynamic pressure so applied is converted into a static pressure on thestationary flow passage 4 which is provided with thediffuser vane 7 and thereturn vane 8. Thereby, the working fluid turns into the high-pressure working fluid, the pressure of the high-pressure working fluid is increased as the fluid sequentially flows into the next-stage impeller 2, and the high-pressure working fluid which has been discharged from the final-stage impeller 2 is fed to the demander and so forth under pressure. - Part of the working fluid which flows through within the
turbomachine 1 leaks to the outside through the gap parts between the stationary part such as thecasing 5 and so forth and therotor 3, that is, the gap between the outer circumferential surface of themouth ring part 2a of theimpeller 2 and the stationary part, the gap between the outer circumferential surface of thecylindrical part 2b of theimpeller 2 and the stationary part, the gap between the outer circumferential surface of thebalance drum 10 and the stationary part and so forth which have been described before. - The labyrinth
shaft sealing devices 9 are respectively provided in the aforementioned respective gap parts in order to reduce these leakage flows. That is, the wearingring 9a is provided on themouth ring part 2a at the entrance of theimpeller 2, thestage bush 9b is provided on thecylindrical part 2b on the rear face of theimpeller 2, and the balance drumshaft sealing device 9c is provided on a part of thebalance drum 10 on the rear face of the final-stage impeller 2 respectively. - Next, configurations of these shaft sealing devices will be described using
FIG. 2 and FIG. 3. FIG. 2 is a diagram illustrating the inner surface shape of the shaft sealing device in theturbomachine 1 illustrated inFIG. 1 , that is, a main part development diagram illustrating theshaft sealing device 9 by developing theshaft sealing device 9 in the circumferential direction, andFIG. 3 is a sectional diagram on arrow along the III-III line inFIG. 2 . An arrow which indicates the circumferential direction matches a rotation direction. The same shall apply hereinafter. In addition, the leakage flow has a swirling component and therefore flows into thedevice 9 in a state of inclining from the axial direction to the circumferential direction. - Incidentally, as the labyrinth
shaft sealing devices 9 which are provided in theturbomachine 1, the wearingring 9a which has been provided on themouth ring part 2a at the entrance of theimpeller 2, thestage bush 9b which has been provided on thecylindrical part 2b on the rear face of theimpeller 2, and the balance drumshaft sealing device 9c which has been provided on the part of thebalance drum 10 on the rear face of the final-stage impeller 2 are provided as described before. In the present embodiment, the inner surface shapes of the above-mentionedshaft sealing devices 9a to 9c are made the same as one another and theshaft sealing device 9 illustrated inFIG. 2 and FIG. 3 has a structure which is commonly applied to the wearingring 9a, thestage bush 9b, and the balance drumshaft sealing device 9c which have been described above. Therefore, in the following, theshaft sealing devices - As illustrated in
FIG. 2 , many grooves which are parallel with the axial direction of therotor 3, that is,axial grooves 11 are provided in an inner surface of theshaft sealing device 9 in the present embodiment. Describing in more detail, an axial groove group A (A1, A2, A3, ,... and A8) which has been configured by a plurality (four grooves in this embodiment) of theaxial grooves 11 which have been intermittently arranged on the same straight line which is parallel with the axial direction of therotor 3 with aland part 12 being interposed between theadjacent grooves 11 is provided in the inner surface of theshaft sealing device 9. The axial groove groups A are adjacently arranged in a plurality of lines in the circumferential direction of the inner surface of theshaft sealing device 9. In the embodiment illustrated inFIG. 2 , eight axial groove groups A1, A2, ... and A8 are provided in the circumferential direction in an illustrated range thereof as the plurality of lines of the axial groove groups which have been adjacently arranged in the circumferential direction. In addition, the plurality of axial groove groups A1, A2, ... and A8 which have been adjacently arranged in the circumferential direction are arranged to be parallel with or almost parallel with one another. - In addition, in the embodiment illustrated in
FIG. 2 , the plurality ofaxial grooves 11 which configure theshaft sealing device 9 are provided so as to form a staggered arrangement that the positions of the adjacent grooves deviate from each other in both of the circumferential direction and the axial direction of the rotor. Further, the plurality ofaxial grooves 11 which are arranged in a staggered state each is formed into a rectangular shape that a length in the axial direction becomes longer than a length in the circumferential direction, the plurality ofaxial grooves 11 are arranged so as to partially overlap one another in the circumferential direction, and the respectiveaxial grooves 11 in each of the axial direction groove groups A1, A2, ... and A8 are configured so as to not overlap theaxial grooves 11 in the other axial groove groups in the axial direction. - It is possible to easily machine each of the
axial grooves 11 which are provided in theshaft sealing device 9 by pressing a circular tool such as, for example, an end mil and so forth against the inner surface of theshaft sealing device 9, and it is possible to form semi-circular (an arc-shaped) grooves which are parallel with one another in the axial direction by a plural number and intermittently with ease as illustrated inFIG. 3 . A length of theland part 12 which is favorable in a case of handling the liquid as the working fluid is sufficiently ensured by intermittently forming theaxial grooves 11 and thereby it becomes possible to produce with ease theshaft sealing device 9 that theland part 12 has a thickness. It becomes possible to effectively reduce an amount of the leakage flow which leaks from the shaft sealing device in the axial direction by sufficiently ensuring the length of theland part 12. - On the other hand, owing to provision of a configuration that many
axial grooves 11 which are long in the axial direction and short in the circumferential direction have been arranged in the circumferential direction in the inner surface of theshaft sealing device 9, it is possible to reduce an amount of the working fluid which escapes in the circumferential direction when displacing therotor 3, in the working fluid which has flown into theaxial grooves 11, and thereby it is possible to improve the vibration damping property of theshaft sealing device 9. - In addition, since the plurality of axial groove groups A (A1, A2, . .. and A8) are arranged in the circumferential direction in the inner surface of the
shaft sealing device 9 and the respectiveaxial grooves 11 in the respective axial groove groups A are arranged in the staggered state so as to partially overlap one another in the circumferential direction, the leakage flow alternately passes over parts of theland parts 12 and theaxial grooves 11. Therefore, it is possible to effectively suppress a swirling-direction flow which would cause generation of the unstable fluid force. - That is, since it is possible to suppress flowing of the leakage flow which flows into the
shaft sealing device 9 in the axial direction by turning into the swirling flow which swirls along the rotation direction of therotor 3, it is possible to reduce generation of the unstable flow force which would further encourage the swirling movement which works in the circumferential direction due to vibration relative to therotor 3 and thereby it is possible to suppress generation of an unstable vibration in therotor 3. - Moreover, according to the present embodiment, although most of the leakage flow which is directed in the axial direction alternately passes over the parts of the
land parts 12 and theaxial grooves 11, theland part 12 has a sufficient thickness (for example, a thickness which corresponds to at least a half of the length of the axial groove 11) in the axial direction and therefore the viscous friction generated when the leakage flow flows over thisland part 12 becomes large and it is also possible to reduce the axial-direction flow owing to abrupt expansion of the leakage flow passage when the leakage flow flows into theaxial groove 11. - Incidentally, since the
axial groove 11 in the above-mentionedembodiment 1 is formed into the rectangular shape that the length in the axial direction becomes longer than the length in the circumferential direction, it is possible to more increase the effect of suppressing turning of the leakage flow which has flown into theshaft sealing device 9 into the swirling flow. However, an aspect ratio of the axial-direction width to the circumferential-direction width of theaxial groove 11 is limited to the aspect ratio which allows formation of the axial groove into the rectangular shape which is long in the axial direction. - In addition, although it is preferable to apply the above-mentioned
shaft sealing device 9 to all of the shaft sealing devices 9 (the wearingring 9a, thestage bush 9b and the balance drumshaft sealing device 9c) of theturbomachine 1, the above-mentionedshaft sealing device 9 may be applied to at least one of theshaft sealing devices 9 and it is effective to apply the present invention, in particular, to theshaft sealing device 9 for a high-pressure part that the unstable fluid force and the leakage amount become large. - Next, modified embodiments of the
turbomachine 1 of the above-mentionedembodiment 1 will be described usingFIG. 4 to FIG. 13 . Since, in the respective drawings, the parts to which the same numerals as those inFIG. 1 to FIG. 3 are assigned indicate the same or corresponding parts and the overall configuration of theturbomachine 1 is the same as the configuration inFIG. 1 which has been described in the above-mentionedembodiment 1, description of the overall configuration of theturbomachine 1 is omitted and only parts which are different in configuration from those inFIG. 1 to FIG. 3 in theshaft sealing device 9 will be described. - A first modified embodiment of the
shaft sealing device 9 in the above-mentionedembodiment 1 will be described with reference toFIG. 4 and FIG. 5. FIG. 4 is a diagram illustrating the first modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram which corresponds toFIG. 2 , andFIG. 5 is a sectional diagram on arrow along the V-V line inFIG. 4 . - While in the embodiment illustrated in
FIG. 2 , the plurality ofaxial grooves 11 which configure theshaft sealing device 9 are provided to be arranged in the staggered state in both of the circumferential direction and the axial direction of therotor 3, in this first modified embodiment, the plurality ofaxial grooves 11 which are parallel with one another in the axial direction and are formed into the rectangular shape are arrayed in a grid form that the positions of the adjacent axial grooves become the same as each other (that is, are on the same straight line) as illustrated inFIG. 4 . - In the present embodiment, the
axial grooves 11 may be arrayed in the grid form in this way. In this case, since the plurality ofaxial grooves 11 are arranged side by side (on the same straight line) respectively in the axial direction and in the circumferential direction, eachland part 12 which is the part where theaxial grooves 11 are not present is formed continuously (that is, so as to extend) in the circumferential direction. For this reason, the effect of suppressing turning of the leakage flow which flows into theshaft sealing device 9 into the swirling flow which swirls along the rotation direction of the rotor is reduced. However, work for positioning the tool and the material when machining theaxial grooves 11 is reduced owing to provision of the configuration of this first modified embodiment and therefore it is possible to obtain an effect of greatly improving productivity. - A second modified embodiment of the
shaft sealing device 9 in the above-mentionedembodiment 1 will be described with reference toFIG. 6 and FIG. 7. FIG. 6 is a diagram illustrating the second modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram which corresponds toFIG. 2 andFIG. 7 is a sectional diagram on arrow along the VII-VII line inFIG. 6 . - While the embodiment that the axial-direction section of the
axial groove 11 which is long in the axial direction has been formed into the semicircular arc-shape is illustrated inFIG. 2 , in this second modified embodiment, the axial-direction section of theaxial groove 11 is formed into a rectangular shape with rounded corners as illustrated inFIG. 7 . It is possible to form the axial-direction section of theaxial groove 11 into shapes other than the arc shape in this way, such as, for example, a rectangular shape, an elliptical shape, a trapezoidal shape, a triangular shape and so forth, not limited to the arc shape and the leakage flow reduction effect and the unstable fluid force reduction effect which are the same as the above are obtained. Incidentally, such an advantage that it is possible to easily perform machining of eachaxial groove 11 is obtained by forming the axial-direction section of eachaxial groove 11 into the arc shape as illustrated inFIG. 3 . - A third modified embodiment of the
shaft sealing device 9 in the above-mentionedembodiment 1 will be described with reference toFIG. 8 and FIG. 9. FIG. 8 is a diagram illustrating the third modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram which corresponds toFIG. 2 andFIG. 9 is a sectional diagram on arrow along the IX-IX line inFIG. 8 . - While the embodiments that the
axial grooves 11 of the same shape and the same size have been provided in theshaft sealing devices 9 have been described in the above-mentionedFIG. 2 to FIG. 7 , in this third modified embodiment, theaxial grooves 11 are configured by two kinds of the grooves, that is, alarge groove 11a which is large in axial-direction and radial-direction sizes and asmall groove 11b which is smaller in the axial-direction and radial-direction sizes as illustrated inFIG. 8 and FIG. 9 . It is favorable to arrange thelarge grooves 11a one by one every time severalsmall grooves 11b are arranged in the axial direction. In the embodiment illustrated inFIG. 8 and FIG. 9 , theaxial grooves large groove 11a is arranged one by one every time thesmall grooves 11b are arranged two by two in the axial direction. Also the respective axial groove groups A1, A2, ... and A8 which are arranged in the plural number in the circumferential direction are configured in the same way. - Since it is possible for the
large grooves 11a to more effectively suppress growing of the swirling flow which is the cause for generation of the unstable fluid force by obstructing uniformity of the flow, it is possible to improve the effect of reducing the unstable fluid force. Incidentally, the number of the kinds of theaxial grooves 11 is not limited to two and three or more kinds of axial grooves which are different from one another in axial-direction and radial-direction sizes may be configured as theaxial grooves 11. - A fourth modified embodiment of the
shaft sealing device 9 in the above-mentionedembodiment 1 will be described with reference toFIG. 10 and FIG. 11. FIG. 10 is a diagram illustrating the fourth modified embodiment of theshaft sealing device 9 in theturbomachine 1 illustrated inFIG. 1 , that is, the diagram which corresponds toFIG. 2 andFIG. 11 is a sectional diagram on arrow along the XI-XI line inFIG. 10 . - The embodiments that the aforementioned
axial grooves 11 are formed as the grooves which are parallel with one another in the axial direction and also the respective axial groove groups A1, A2, ... and A8 which are provided in the plural number in the circumferential direction are arranged in parallel with one another respectively in the axial direction have been described in theshaft sealing devices 9 illustrated in the above-mentionedFIG. 2 to FIG. 9 . In contrast, in this fourth modified embodiment, theaxial grooves 11 are provided by inclining them from the axial direction to the rotation direction (the circumferential direction) of themotor 3 and also the respective axial groove groups A1, A2, ... and A8 which are provided in the plural number in the circumferential direction are arranged so as to be parallel with one another by respectively inclining the axial groove groups from the axial direction to the rotation direction of therotor 3. - Since it is possible to proximate the direction that the
axial grooves 11 are directed to the direction that the leakage flow flows into theshaft sealing device 9 by inclining theaxial grooves 11 and the axial groove groups A1, A2, .. and A8 which configure theshaft sealing device 9 from the axial direction to the rotation direction of therotor 3 in this way, it is possible to more effectively decelerate a flow velocity of the leakage flow. Accordingly, it is possible to more reduce the leakage flow and it is also possible to effectively suppress the unstable fluid force. - Incidentally, since it is desirable for the
shaft sealing device 9 to suppress the leakage flow as much as possible, it is a requirement that an angle formed by the direction that theaxial grooves 11 are directed or the direction that the axial groove groups A1, A2, ... and A8 are directed and the axial direction of therotor 3 be less than 45 degrees, that is, an angle formed by the direction that theaxial grooves 11 are directed or the direction that the axial groove groups A1, A2, ... and A8 are directed and the rotation direction of therotor 3 be at most 45 degrees. In addition, in the description of the present invention, the grooves and the groove groups whose angle relative to the axial direction of therotor 3 is less than 45 degrees are also called the axial grooves and the axial groove groups respectively. - A fifth modified embodiment of the
shaft sealing device 9 in the above-mentionedembodiment 1 will be described with reference toFIG. 12 and FIG. 13. FIG. 12 is a diagram illustrating the fifth modified embodiment of the shaft sealing device in the turbomachine illustrated inFIG. 1 , that is, the diagram which corresponds toFIG. 2 andFIG. 13 is a sectional diagram on arrow along the XIII-XIII line inFIG. 12 . - The fifth modified embodiment is an embodiment that the aforementioned
shaft sealing device 9 of theembodiment 1 illustrated inFIG. 2 and FIG. 3 is partially modified, the basic configuration thereof is the same as that illustrated inFIG. 2 and FIG. 3 and therefore description will be made focusing on different points. - In the fifth modified embodiment, the plurality of
axial grooves 11 are the same as those in the embodiment illustrated inFIG. 2 and FIG. 3 in the point that the plurality ofaxial grooves 11 are arranged in the staggered state in the axial direction of therotor 3. However, while in the embodiment illustrated inFIG. 2 and FIG. 3 , theaxial grooves 11 which are arranged on the same straight line in the axial direction are configured so as not overlap theaxial grooves 11 on another same straight line, in the fifth modified embodiment, theaxial grooves 11 which are arranged on the same straight line in the axial direction are configured so as to partially overlap the otheraxial grooves 11 which are arranged adjacently to the above-mentionedaxial grooves 11 in the circumferential direction or theaxial grooves 11 which are arranged on another same straight line. - Describing with reference to
FIG. 12 , for example, theaxial grooves 11 in the axial groove group A1 are arranged so as to partially overlap theaxial grooves 11 in the axial groove group A2 (in the embodiment inFIG. 12 , only one groove is illustrated) which is adjacent to the axial groove group A1 in the circumferential direction. The same applies to other axial groove groups A3 to A12. In addition, the respectiveaxial grooves 11 in one of the aforementioned respective axial groove groups A1 to A12 are configured so as not to overlap, in the circumferential direction, theaxial grooves 11 in another one of the axial groove groups A1 to A12 which is adjacent to the above-mentioned axial groove group in the circumferential direction. Accordingly, in this fifth modified embodiment, eachland part 12 is provided continuously (that is, so as to extend) in the circumferential direction. Other configurations are the same as those of the embodiment illustrated inFIG. 2 and FIG. 3 . - According to the fifth modified embodiment, the
axial grooves 11 are configured so as to partially overlap one another in the axial direction and therefore an effect of more reducing the leakage flow in the axial direction is obtained. - As described above, according to the embodiments which have been described above, since in the shaft sealing device, the plurality of
axial grooves 11 which are long in an axial direction and short in a circumferential direction of the rotor, which have been intermittently arranged in the axial direction and the circumferential direction of the rotor with the land part being interposed between the adjacentaxial grooves 11, and which are provided in the inner circumferential surface thereof, it is possible to obtain the turbomachine which is capable of reducing the leakage of the working fluid in the shaft sealing device of the turbomachine which handles the liquid as the working fluid and is also capable of reducing the unstable fluid force which acts on the rotor. - Incidentally, the present invention is not limited to the above-mentioned embodiments. For example, although in the above-mentioned embodiments, the case where the present invention has been applied to the uniaxial multistage centrifugal pump as the turbomachine has been described by way of example, the present invention is not limited to the uniaxial multistage centrifugal pump and is also applicable to a single-stage centrifugal pump, a reversible pump turbine, a hydraulic turbine and so forth similarly.
- In addition, it is also possible to replace part of the configuration of the embodiments which have been described above with the configuration of another embodiment and it is also possible to add the configuration of another embodiment to the configuration of the embodiments which have been described above. Further, the above-mentioned embodiments have been described for comprehensibly describing the present invention and is not necessarily limited to the turbomachine which includes all of the configurations which have been described above. The scope of the present invention is solely defined by the appended claims.
Claims (12)
- A turbomachine (1) comprising:a rotor (3) having an impeller (2);a bearing which rotatably supports the rotor (3);a casing (5) which contains the rotor (3) therein and forms a stationary flow passage (4); anda shaft sealing device (9) which reduces leakage of a working fluid through a gap part between the casing (5) and the rotor (3), wherein the working fluid is a liquid;characterised in that the turbomachine comprises:
a plurality of axial grooves (11; 11a, 11b) which are long in an axial direction and short in a circumferential direction of the rotor (3), which have been intermittently arranged in the axial direction and the circumferential direction with a land part (12) interposed between adjacent axial grooves (11; 11a, 11b), and which are provided in an inner circumferential surface of the shaft sealing device (9). - The turbomachine (1) according to claim 1, wherein the axial grooves (11; 11a, 11b) are configured in a rectangular shape which is long in the axial direction, and the plurality of axial grooves (11; 11a, 11b) are arranged in parallel with one another.
- The turbomachine (1) according to claim 2, wherein the plurality of axial grooves (11; 11a, 11b) are arranged in a staggered state at least in one direction of the axial direction and the circumferential direction of the rotor (3).
- The turbomachine (1) according to claim 3, wherein the plurality of axial grooves (11; 11a, 11b) are arranged in the staggered state in the axial direction of the rotor (3), and the axial grooves (11; 11a, 11b) which are arranged in the staggered state are configured so as to partially overlap one another in the axial direction.
- A turbomachine (1) according to claim 1, wherein
an axial groove group (A1, A2, A3, ..., A8) which includes axial grooves of the plurality of axial grooves (11; 11a, 11b) which have been intermittently arranged on the same straight line directed in an axial direction with the land part (12) being interposed between adjacent axial grooves (11; 11a, 11b), is provided in an inner circumferential surface of the shaft sealing device (9), and
a plurality of the axial groove groups are adjacently arranged in the circumferential direction, and the plurality of axial groove groups which have been adjacently arranged in the circumferential direction are arranged so as to be parallel with one another with the land part (12) being interposed between the adjacent axial groove groups. - The turbomachine (1) according to claim 5, wherein the plurality of axial grooves (11; 11a, 11b) are arranged in a staggered state in at least one direction of the axial direction and the circumferential direction of the rotor (3).
- The turbomachine (1) according to claim 6, wherein the plurality of axial grooves (11; 11a, 11b) are arranged in the staggered state in the circumferential direction of the rotor (3), and the axial grooves (11; 11a, 11b) which are arranged in the staggered state are configured so as to partially overlap one another in the circumferential direction.
- The turbomachine (1) according to claim 5, wherein the axial grooves (11; 11a, 11b) which configure each of the axial groove groups are configured by grooves (11a, 11b) of a plurality of sizes which are mutually different in length in the axial direction.
- The turbomachine (1) according to claim 8, wherein the axial grooves (11; 11a, 11b) which configure each of the axial groove groups are configured by small grooves (11b) and large grooves (11a) which are mutually different in length in the axial direction, and one large groove (11a) is arranged every time several small grooves (11b) are arranged in the axial direction.
- The turbomachine (1) according to claim 5, wherein the plurality of axial grooves (11; 11a, 11b) are arrayed in a grid form.
- The turbomachine (1) according to claim 5, wherein the shape of an axial section of the axial groove (11; 11a, 11b) is configured in an arc shape or a rectangular shape with rounded corners.
- The turbomachine (1) according to claim 5, wherein the plurality of axial grooves (11; 11a, 11b) are provided by inclining the axial grooves (11; 11a, 11b)from the axial direction to a rotation direction of the rotor (3), and the respective axial groove groups which are arranged in a plural number in the circumferential direction are arranged so as to be parallel with one another by respectively inclining by less than 45 degrees the axial groove groups from the axial direction to the rotation direction of the rotor (3).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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JP2016046891A JP2017160861A (en) | 2016-03-10 | 2016-03-10 | Turbo machine |
Publications (2)
Publication Number | Publication Date |
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EP3217016A1 EP3217016A1 (en) | 2017-09-13 |
EP3217016B1 true EP3217016B1 (en) | 2019-05-08 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP17000320.6A Active EP3217016B1 (en) | 2016-03-10 | 2017-03-01 | Turbomachine |
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US (1) | US10718348B2 (en) |
EP (1) | EP3217016B1 (en) |
JP (1) | JP2017160861A (en) |
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CN108730196A (en) * | 2018-08-07 | 2018-11-02 | 安德里茨(中国)有限公司 | Sectional type multi-stage pump |
US11773738B2 (en) * | 2021-12-09 | 2023-10-03 | Rtx Corporation | Radial lift seal |
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JP2017160861A (en) | 2017-09-14 |
EP3217016A1 (en) | 2017-09-13 |
US10718348B2 (en) | 2020-07-21 |
US20170260991A1 (en) | 2017-09-14 |
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